EP3105506B1 - Module de brûleur en veine - Google Patents

Module de brûleur en veine Download PDF

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Publication number
EP3105506B1
EP3105506B1 EP15706856.0A EP15706856A EP3105506B1 EP 3105506 B1 EP3105506 B1 EP 3105506B1 EP 15706856 A EP15706856 A EP 15706856A EP 3105506 B1 EP3105506 B1 EP 3105506B1
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EP
European Patent Office
Prior art keywords
angle
burner module
plane
section
stream
Prior art date
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Active
Application number
EP15706856.0A
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German (de)
English (en)
French (fr)
Other versions
EP3105506A1 (fr
Inventor
Fouad SAID
Louis Ricci
Yannick BOUDET
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Fives Pillard SA
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Fives Pillard SA
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/34—Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants
    • F23R3/20—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants incorporating fuel injection means
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D14/00—Burners for combustion of a gas, e.g. of a gas stored under pressure as a liquid
    • F23D14/20—Non-premix gas burners, i.e. in which gaseous fuel is mixed with combustion air on arrival at the combustion zone
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/35—Combustors or associated equipment
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/14—Special features of gas burners
    • F23D2900/14003—Special features of gas burners with more than one nozzle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/21—Burners specially adapted for a particular use
    • F23D2900/21003—Burners specially adapted for a particular use for heating or re-burning air or gas in a duct
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
    • F23R3/18—Flame stabilising means, e.g. flame holders for after-burners of jet-propulsion plants

Definitions

  • the present invention relates to an air stream burner used for the direct heating of air or combustion gas from turbines or engines and more particularly to the stream burner module whose juxtaposition side by side on ramps constitutes the burner in vein.
  • This type of burner works with the combustion gases of a turbine (called TEG) or an engine as oxidizer which have an oxygen rate (on wet fumes) lower than the ambient air, a temperature higher than the ambient temperature and generally, a relatively low speed at the passage of the burner and as fuel natural gas, shale gas, petroleum gas or gas from industrial processes.
  • TEG turbine
  • oxidizer which have an oxygen rate (on wet fumes) lower than the ambient air, a temperature higher than the ambient temperature and generally, a relatively low speed at the passage of the burner and as fuel natural gas, shale gas, petroleum gas or gas from industrial processes.
  • a burner having the characteristics of the preamble of claim 1 is described in document US 3732059 .
  • turbine gases are characterized by increasingly low oxygen contents in wet fumes (between 9% and 13%) and more variable and higher temperatures (between 350 ° C and 700 ° C). ).
  • controlling the lengths of the flame is a major issue since it makes it possible to control the downstream temperature profile while minimizing the lengths of the sheaths, which are very expensive.
  • Known vein burner modules do not provide the mixing and local depressions necessary to control carbon monoxide (CO) emissions and flame stability under these difficult conditions, in particular at low TEG speeds.
  • the air stream burner module comprises a supply duct having a substantially circular section and an axis, fuel injection orifices located on the duct and intended to produce a flame, orifices of injection of oxidizer and fins, or caps, forming a structure called module or block) and arranged symmetrically with respect to a fuel flow plane P upstream of the burner module and laterally on the duct on each side of the orifices d fuel injection, at least two fuel injection orifices in a section of the duct that they have an axis which makes an angle ⁇ with the plane fuel flow.
  • the gas is injected into several orifices located in at least two divergent planes.
  • the angle ⁇ is between 10 ° and 30 °.
  • the injection orifices have a section of different size on each side of the plane P.
  • the gas injection orifices of the same module are arranged symmetrically with respect to the flow plane P. and can have different sections and consequently gas flow rates between the top and the bottom (if the plane P is horizontal).
  • the two fuel injection orifices have an axis which crosses on the axis of the duct.
  • At least two other secondary fuel injection orifices form an angle ⁇ with the fuel flow plane and that the angle ⁇ is greater than the angle ⁇ . This allows a staged TEG arrival which promotes recirculation and ensures an optimal fuel / oxidizer ratio.
  • the secondary fuel injection orifices of angle ⁇ have a section representing 5% to 20% of the total section of the fuel injection orifices.
  • the vein burner module comprises fins forming an angle ⁇ with the fuel flow plane.
  • the angle ⁇ is between 2 ⁇ and 3 ⁇ .
  • a large module (block) size is thus obtained which protects the flared development of the flame and the internal recirculations linked to the angular injection. This maintains a hot zone which limits the formation of CO. There is thus the creation of a significant local stabilization depression even during operation with low TEG speeds.
  • the angle of the caps equal to 2 to 3 times the gas injection angle allows both to generate the spaces necessary for the correct introduction of the TEGs and their mixing with the gas jets in the combustion zone and development of the main eddy.
  • the fins have a section having oxidizer injection openings.
  • a stepped TEG inlet promotes recirculation and ensures an optimal fuel / oxidizer ratio, it is achieved through the openings which are preferably slot-shaped and whose number and section are determined so as to obtain a low% of the flow stoichiometric air (of the order of 5 to 25%).
  • the openings have a section of between 3 to 15% of the section of the fins.
  • the passage section of these openings may vary depending on the velocity and oxygen characteristics of the TEGs.
  • the openings have a section of different size on each side of the plane P.
  • the sections of these openings and consequently of the TEG flow rates passing through them may be different between the top and the bottom.
  • the openings include deflection elements forming an angle ⁇ with the fuel flow plane.
  • the angle ⁇ is substantially equal to the angle ⁇ .
  • the deflection elements give the passage openings an angle substantially identical to the angle of injection of the gas.
  • the section of the openings increases with the distance between the orifices to optimize the gradual introduction of air into the flame and reduce the formation of CO.
  • a shield placed between the duct and the flame, said shield having holes situated in line with the injection orifices.
  • This arrangement accelerates the TEG / gas mixture and improves the stability of the flame.
  • the cross section of the premix port located in the shield is 15 to 40 times the cross section of the gas outlet port.
  • the premix orifice is located at a distance from the gas orifice between 0.1 and 0.3 times the diameter of the tube.
  • the holes are located on a wall of the shield which has an angle 8 with respect to the axis of the injection orifices. This arrangement promotes the suction of the oxidizer by the gas jet.
  • the angle 8 is substantially equal to 90 °. This arrangement promotes local turbulence and therefore flame stability despite the low oxygen levels, temperature and TEG velocity.
  • the burner module comprises baffles located in an external part of the burner module and that said baffles have a rim which has an angle equal and opposite to that of the deflection element located furthest from the duct. .
  • This specially designed shape of the baffles or ends of the closure plates makes it possible to obtain a flow of the TEGs around the modules, parallel or almost parallel to the gas flow plane in order to limit the formation of CO by the quenching effect.
  • This shape is characterized by symmetry between the end of the modules and the end of the blocks.
  • the burner module has a surface projected onto a plane perpendicular to the flow of the TEGs and is between 0.1 and 0.3 m 2 / MW.
  • the size of the module is defined by its surface projected onto a plane perpendicular to the flow of the TEGs and this size is particularly advantageous for an upstream oxygen level of between 9% and 14% on wet fumes.
  • the combustion process according to the invention comprising a stream burner module with at least one of the preceding characteristics, such that the oxidizer has an oxygen content of less than 21%.
  • a premix is made in the space between the duct and the shield.
  • the invention also relates to a vein burner made up of modules having the above characteristics.
  • two adjacent modules have injection orifices with sections of different size on each side of the plane P alternately.
  • a complementary turbulence is created in the plane perpendicular to the flow plane P and parallel to the axis of the tube. This additional turbulence accelerates the mixing of the gas with the TEGs and shortens the flame lengths.
  • the ratio of the sections between the top and bottom orifices can vary between 0.25 and 4 and advantageously between 0.5 and 2.
  • two adjacent modules have openings of different size on each side of the plane P alternately.
  • a complementary turbulence is created in the plane perpendicular to the flow plane P and parallel to the axis of the tube. This additional turbulence accelerates the mixing of the gas with the TEGs and shortens the flame lengths.
  • the ratio of the sections between the top and bottom openings can vary between 0.25 and 4 and advantageously between 0.5 and 2.
  • each duct burner module comprises a duct 2 constituting a fuel supply duct.
  • Each burner module 1 comprises fins 3 arranged on either side of the duct 2, in which the fuel 4 flows, symmetrically with respect to a plane Pet with an angle ⁇ .
  • the fuel flows through injection orifices 20 arranged on either side of the plane P symmetrically.
  • the duct 2 is covered with a shield 5 pierced with holes 50 placed opposite the orifices 20.
  • the fins 3 on one side are arranged more or less distant from the duct 2.
  • the fin 30 is the closest, the fin 31 is located in an intermediate way while the fin 32 is placed outermost. or the furthest from the duct 2.
  • the fins 30, 31, 32 are separated from each other by openings 33. It is of course possible to have more or less than three fins.
  • the fuel 4 arrives through line 2, it is injected into combustion chamber 6 through orifices 20.
  • These orifices 20 are oriented at an angle ⁇ with respect to the fuel flow plane P. This angle makes it possible to delimit a space without the addition of fuel and without the addition of oxidizer, which is favorable to the internal recirculation of the combustion gases 4 inside the flame as illustrated. figure 1 by creating an eddy or a main turbulence 40 and which brings back to the center a large part of the burnt gases.
  • the angle ⁇ of the fins is substantially between 2 ⁇ and 3 ⁇ .
  • the injection orifices 20 of the same module 1 have size sections and consequently fuel flow rates 4 which are different on each side of the plane P, ie, if P is horizontal, between the top and the bottom.
  • a radial component 41 is created at the bottom.
  • main turbulence 40 This radial component 41 shortens the flame lengths.
  • the ratio of the sizes of the sections between the top and bottom orifices 20 can vary between 0.25 and 4 and advantageously between 0.5 and 2.
  • the openings 33 of the TEGs of the same module 1 have sections of different size between the top and the bottom of the plane P.
  • openings 33 of increased size at the bottom and modules with openings 33 of increased size at the top we create or increase the complementary radial component 41 to the turbulence 40 which shortens the flame lengths
  • the figure 2 shows the circulation of the TEGs 7 or turbine gases which enter through the openings 33 at an angle ⁇ thanks to the deflection elements 34. This makes it possible to create a stabilization zone 70.
  • the baffles 8 have one end having a rim 80 which cooperate with the deflection element 34 of the fin 32 to allow a flow of the TEGs 7 around the burner modules 1 parallel or almost parallel to the plane P.
  • the space between the deflection element 34 of the fin 32 and the rim 80 is larger than the size of the openings 33.
  • the rim 80 forms an angle ⁇ .
  • conduit 2 and shield 5 circulates TEGs (cf. figure 3 ) which are sucked through the orifice 20, the diameter of which is preferably greater than that of the holes 50, towards the combustion chamber 6 and thus allows a premixing of the fuel 4.
  • the shield 5 has flat walls 52 which are more favorable to the creation of eddies.
  • the holes 50 allow the injection of gas at an angle 8 with respect to the wall 52 of the shield 5.
  • the duct 2 has secondary injection openings 21 which allows the fuel 4 to be injected at an angle greater than ⁇ .
  • Each secondary opening 21 is placed opposite a secondary hole 51 of the shield 5.
  • the quantity of fuel 4 injected is 80 to 95% through the orifices 20 and the holes 50 and from 5 to 20% through the holes. secondary holes 21 and secondary holes 51.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Gas Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
EP15706856.0A 2014-02-12 2015-01-26 Module de brûleur en veine Active EP3105506B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1451064A FR3017445B1 (fr) 2014-02-12 2014-02-12 Module de bruleur en veine
PCT/FR2015/050176 WO2015121559A1 (fr) 2014-02-12 2015-01-26 Module de brûleur en veine

Publications (2)

Publication Number Publication Date
EP3105506A1 EP3105506A1 (fr) 2016-12-21
EP3105506B1 true EP3105506B1 (fr) 2021-07-07

Family

ID=50513298

Family Applications (1)

Application Number Title Priority Date Filing Date
EP15706856.0A Active EP3105506B1 (fr) 2014-02-12 2015-01-26 Module de brûleur en veine

Country Status (6)

Country Link
US (1) US10378441B2 (ko)
EP (1) EP3105506B1 (ko)
KR (1) KR102330238B1 (ko)
CN (1) CN105992913B (ko)
FR (1) FR3017445B1 (ko)
WO (1) WO2015121559A1 (ko)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US9879862B2 (en) 2013-03-08 2018-01-30 Rolls-Royce North American Technologies, Inc. Gas turbine engine afterburner
BE1024480B1 (nl) * 2016-08-08 2018-03-09 Agrofrost, Naamloze Vennootschap Gasbrander voor sterke luchtstroom
CN107166386B (zh) * 2017-05-09 2019-05-14 华中科技大学 一种防回火的预混燃烧渐扩燃烧器
JP7248744B2 (ja) * 2021-06-28 2023-03-29 三菱重工パワーインダストリー株式会社 ガスバーナ、及びガス焚きボイラ

Family Cites Families (15)

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Publication number Priority date Publication date Assignee Title
US3732059A (en) * 1971-05-28 1973-05-08 Zink Co John Burner for gaseous fuels in reduced oxygen and/or significant velocity atmosphere
US3830620A (en) * 1972-02-22 1974-08-20 Gen Electric Gas burner for heat-recovery steam generator
US4237858A (en) * 1978-01-16 1980-12-09 John Zink Company Thin and flat flame burner
JPS6089610A (ja) 1983-10-21 1985-05-20 Mitsubishi Heavy Ind Ltd ガス焚きダクトバ−ナ装置
JPS6089611A (ja) * 1983-10-24 1985-05-20 Mitsubishi Heavy Ind Ltd ガス焚きダクトバ−ナ装置
FR2588920B1 (fr) 1985-10-23 1987-12-04 Snecma Turboreacteur a postcombustion a injecteurs de postcombustion radiaux individuels
FR2622277B1 (fr) * 1987-10-23 1990-02-23 Mecanique Gle Foyers Turbine S Bruleur a gaz pour le chauffage d'un courant d'air ou autre gaz comburant
FR2770284B1 (fr) * 1997-10-23 1999-11-19 Snecma Accroche-flamme carbure et a refroidissement optimise
US6301875B1 (en) * 2000-05-31 2001-10-16 Coen Company, Inc. Turbine exhaust gas duct heater
US6921261B2 (en) * 2000-09-28 2005-07-26 Maxon Corporation Air-heating gas burner
US6929470B1 (en) * 2002-10-30 2005-08-16 Coen Company, Inc. Low NOx duct burner
US20110219776A1 (en) * 2010-03-15 2011-09-15 General Electric Company Aerodynamic flame stabilizer
EP2442026B1 (de) * 2010-10-15 2016-01-27 Elster GmbH Hochtemperaturbrenner für Brennerbetriebsverfahren mit zwei Betriebszuständen
US20120297784A1 (en) * 2011-05-24 2012-11-29 General Electric Company System and method for flow control in gas turbine engine
US9310072B2 (en) * 2012-07-06 2016-04-12 Hamilton Sundstrand Corporation Non-symmetric arrangement of fuel nozzles in a combustor

Non-Patent Citations (1)

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Title
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Also Published As

Publication number Publication date
WO2015121559A1 (fr) 2015-08-20
CN105992913B (zh) 2018-12-18
EP3105506A1 (fr) 2016-12-21
KR20160122210A (ko) 2016-10-21
FR3017445B1 (fr) 2019-05-24
KR102330238B1 (ko) 2021-11-24
FR3017445A1 (fr) 2015-08-14
US10378441B2 (en) 2019-08-13
US20160356217A1 (en) 2016-12-08
CN105992913A (zh) 2016-10-05

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